[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

EP2385216B1 - Turbinenschaufel mit Gehäuse-Mikrokanälen, die in der Plattform enden - Google Patents

Turbinenschaufel mit Gehäuse-Mikrokanälen, die in der Plattform enden Download PDF

Info

Publication number
EP2385216B1
EP2385216B1 EP11157143.6A EP11157143A EP2385216B1 EP 2385216 B1 EP2385216 B1 EP 2385216B1 EP 11157143 A EP11157143 A EP 11157143A EP 2385216 B1 EP2385216 B1 EP 2385216B1
Authority
EP
European Patent Office
Prior art keywords
platform
turbine engine
side wall
refractory metal
engine component
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP11157143.6A
Other languages
English (en)
French (fr)
Other versions
EP2385216A3 (de
EP2385216A2 (de
Inventor
Douglas C. Jenne
Matthew S. Gleiner
Matthew A. Devore
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2385216A2 publication Critical patent/EP2385216A2/de
Publication of EP2385216A3 publication Critical patent/EP2385216A3/de
Application granted granted Critical
Publication of EP2385216B1 publication Critical patent/EP2385216B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage

Definitions

  • the present disclosure is directed to a turbine engine component having microcircuit cooling passages that cover the initial 10% span of the airfoil portion and originate in the platform and may provide up to 100% coverage along the entire airfoil.
  • Gas turbine engines include a compressor which compresses a gas and delivers it into a combustion chamber.
  • the compressed air is mixed with fuel and combusted, and products of this combustion pass downstream over turbine rotors.
  • Gas turbine engines include a compressor which compresses air and delivers it downstream into a combustion section. The air is mixed with fuel in the combustion section and ignited. Products of this combustion pass downstream over turbine rotors, which are driven to rotate. In addition, static vanes are positioned adjacent to the turbine rotors to control the flow of the products of combustion.
  • the turbine rotors carry blades.
  • the blades and the static vanes have airfoils extending from platforms.
  • the blades and vanes are subject to extreme heat, and thus cooling schemes are utilized for each.
  • Cooling circuits for turbine engine components have been embedded into the airfoil walls (and referred to as microcircuit cooling passages). These cooling circuits however have originated prior to the initial 10% span of an airfoil portion.
  • a turbine engine component having the features of the preamble of claim 1 is disclosed in US 7527475 B1 .
  • a further turbine blade having microcircuit cooling passages is disclosed in EP-A-1882816 .
  • GB-A-768247 discloses a turbine blade in which cooling air is supplied to grooves formed between a blade core and a surrounding sheath.
  • microcircuit cooling passage in an airfoil portion of a turbine engine component which cools the initial 10% span of the airfoil portion to manage stress, gas flow, and heat transfer.
  • Fig. 1 illustrates a portion of a turbine engine 10.
  • the turbine engine 10 has a section which includes a vane 12 having an airfoil portion 14 and a blade 16 having an airfoil portion 18.
  • the area 20 shows the area which is to be discussed herein.
  • Fig. 2 illustrates a portion of a turbine blade 16.
  • the blade 16 has a platform 22, a root portion 24, and an airfoil portion 26.
  • the blade 16 has a pressure side wall 28 and a suction side wall (not shown). Between the pressure side wall 28 and the suction side wall, there are one or more cores or cavities 30 through which a cooling fluid flows.
  • the platform 22 has an upper surface 23 and a lower surface 25.
  • High heat load applications may require one or more cooling circuits or microcircuits embedded within at least one of the pressure side wall 28 and the suction side wall. These cooling circuits provide cooling and shielding from coolant heat pickup.
  • the cooling circuits are formed during casting by using refractory metal cores to form the passages 32, 34, and 36 shown in Figs. 2 and 9 . After the blade 16 has been cast, the cores are chemically removed, leaving the desired cooling circuits.
  • Each of the refractory metal cores 32, 34, and 36 is fabricated so as to create a desired set of fluid passageways with or without a desired set of features such as pedestals for creating turbulence in the cooling flow.
  • the refractory metal cores may be made out of a refractory material such as molybdenum or a molybdenum alloy.
  • the region or area 20 is not covered by any portion of the microcircuit cooling passages 32, 34, and 36. Conversely, this uncovered area 20 along the airfoil root is subject to high thermal gradients.
  • microcircuit cooling passages 32, 34, and 36 can be provided by allowing the microcircuit cooling passages 32, 34, and 36 to end in the region of the platform 22 allowing better management of stress, gas flow and heat transfer.
  • the microcircuit cooling passages terminates in a location 31 between the upper surface 23 and the lower surface 25 such as the mid-region of the thickness T.
  • Fig. 4 is a sectional view of the pressure side taken along lines A - A in Fig. 3 .
  • the microcircuit cooling passage(s) 32, 34 and/or 36 terminate in the vicinity of the platform 22, while being embedded within the pressure side wall 28 within the platform thickness T.
  • Fig. 5 illustrates the suction side wall 29 of a turbine blade 16.
  • Fig. 6 is a sectional view taken along lines B - B in Fig. 5 .
  • One or more microcircuit cooling passages 42 may be embedded within the suction side wall 29. As can be seen from these figures, the cooling passage(s) 42 terminate in the a location 33 between the upper surface 23 and the lower surface 25 of the platform 22 within the platform thickness T.
  • the turbine blade 16 has one or more central cores 44, through which cooling fluid flows.
  • Each respective cooling circuit 60, 62 has an inlet 45 adjacent the terminal end of the cooling circuit in the platform region of the turbine blade which fluidly connects to a respective core 44.
  • the inlet 45 may be formed using any suitable technique known in the art, such as providing a refractory metal core with a curved configuration which forms the inlet 45.
  • the turbine blade 16 may be formed using a lost molding technique as is known in the art.
  • the microcircuit cooling passages 32, 34, 36 and 42 may be formed from a refractory metal or metal alloy such as molybdenum or a molybdenum alloy. Alternatively, each of these microcircuit cooling passages 32, 34, 36 and 42 may be formed from a ceramic or silica material. It is also to be noted that, depending on the size of the cooling passages, e.g., for larger parts and the part, the cooling passages may be formed using conventional ceramic cores in place of some or all of the metal cores.
  • step 100 the refractory metal cores 32, 34, 36 and 42 used to form the cooling passages are manufactured. Any suitable technique may be used to manufacture the cores.
  • step 102 the refractory metal cores are assembled with the main core. The refractory metal cores are positioned so that a terminal end of each refractory core is located in a region where a platform is to be formed.
  • step 104 wax is injected around the assembled cores to form a wax pattern.
  • step 106 the wax pattern, with the cores, is dipped in a slurry which coats the wax pattern and forms a shell. After being formed, the shell is dried. The wax is then melted away to leave the shell to function as a mold.
  • step 108 the turbine engine component is cast by pouring molten material into the mold/shell.
  • the molten metal is allowed to solidify.
  • step 110 the turbine engine component with the cores is removed from the mold.
  • step 112 the main core and the refractory metal cores are removed.
  • the cores may be removed using any suitable technique known in the art.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (11)

  1. Turbinenmotorkomponente (16), umfassend:
    einen Schaufelabschnitt (26), der eine Plattform (22), eine Druckseitenwand (28), eine Saugseitenwand (29) und einen Wurzelabschnitt (24) aufweist;
    mindestens einen Mikrokanalkühldurchlass (32, 34, 36; 42; 60, 62), der innerhalb mindestens einem von der Druckseitenwand (28) und der Saugseitenwand (29) eingebettet ist; und
    mindestens einen zentralen Kern (44), wobei jeder Mikrokanalkühldurchlass (60, 62) einen Einlass (45) aufweist, der mit dem mindestens einen zentralen Kern (44) kommuniziert;
    wobei jeder Mikrokanalkühldurchlass (32, 34, 36; 42; 60, 62) Kühlung innerhalb einer anfänglichen Spanne von 10 % des Schaufelabschnitts (26) bereitstellt;
    wobei die Plattform (22) eine obere Fläche (23), eine untere Fläche (25) und eine Dicke (T) aufweist; dadurch gekennzeichnet, dass:
    jeder Mikrokanalkühldurchlass (32, 34, 36; 42; 60, 62) innerhalb eines beliebigen Abschnitts der Dicke (T) zwischen der oberen Fläche (23) und der unteren Fläche (25) der Plattform (22) endet, und dass der Einlass (45) innerhalb der Plattform (22) eingebettet ist.
  2. Turbinenmotorkomponente nach Anspruch 1, wobei der mindestens eine Mikrokanalkühldurchlass (32, 34, 36; 60) innerhalb der Druckseitenwand eingebettet ist.
  3. Turbinenmotorkomponente nach Anspruch 1, wobei der mindestens eine Mikrokanalkühldurchlass (42; 62) innerhalb der Saugseitenwand (29) eingebettet ist.
  4. Turbinenmotorkomponente nach Anspruch 1, wobei der mindestens eine Kühldurchlass einen ersten Mikrokanalkühldurchlass (42; 62), der innerhalb der Saugseitenwand (29) eingebettet ist, und einen zweiten Mikrokanalkühldurchlass (32, 34, 36; 60), der innerhalb der Druckseitenwand (28) eingebettet ist, beinhaltet.
  5. Turbinenmotorkomponente nach einem vorhergehenden Anspruch, wobei jeder Mikrokanalkühldurchlass (32, 34, 36; 42; 60, 62) in einem Mittelbereich der Dicke (T) der Plattform (22) endet.
  6. Verfahren zum Bilden einer Turbinenmotorkomponente (16) nach Anspruch 1, die folgenden Schritte umfassend:
    Bereitstellen eines Hauptkerns zum Bilden der Turbinenmotorkomponente (16), welche die Plattform (22) aufweist;
    Bereitstellen mindestens eines feuerfesten Metallkerns, der ausgelegt ist, um den mindestens einen Mikrokanalkühldurchlass (32, 34, 36; 42; 60, 62) zu bilden; gekennzeichnet durch
    Positionieren des mindestens einen feuerfesten Metallkerns relativ zu dem Hauptkern, sodass sich ein terminales Ende des mindestens einen feuerfesten Metallkerns innerhalb eines beliebigen Abschnitts der Dicke (T) zwischen der oberen Fläche (23) und der unteren Fläche (25) der Plattform (22) befindet und innerhalb der Plattform (22) eingebettet ist.
  7. Verfahren nach Anspruch 6, wobei der Positionierungsschritt das Positionieren des mindestens einen feuerfesten Metallkerns an einer Stelle umfasst, an der der mindestens eine feuerfeste Metallkern innerhalb einer Druckseitenwand (28) der Turbinenmotorkomponente (16) eingebettet wird.
  8. Verfahren nach Anspruch 6, wobei der Positionierungsschritt das Positionieren des mindestens einen feuerfesten Metallkerns an einer Stelle umfasst, an der der mindestens eine feuerfeste Metallkern innerhalb einer Saugseitenwand (29) der Turbinenmotorkomponente (16) eingebettet wird.
  9. Verfahren nach einem der Ansprüche 6 bis 8, wobei der Positionierungsschritt das Positionieren des mindestens einen feuerfesten Metallkerns, sodass jeder feuerfeste Metallkern in einem Mittelbereich der Dicke (T) der Plattform (22) endet, umfasst.
  10. Verfahren nach einem der Ansprüche 6 bis 9, ferner umfassend das Bilden mindestens eines Kühlkanals (32, 34, 36, 42) durch Entfernen des mindestens einen feuerfesten Metallkerns.
  11. Verfahren nach Anspruch 10, ferner umfassend das Entfernen des Hauptkerns, nachdem die Turbinenmotorkomponente (16) gegossen worden ist.
EP11157143.6A 2010-05-06 2011-03-07 Turbinenschaufel mit Gehäuse-Mikrokanälen, die in der Plattform enden Active EP2385216B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/774,771 US9121290B2 (en) 2010-05-06 2010-05-06 Turbine airfoil with body microcircuits terminating in platform

Publications (3)

Publication Number Publication Date
EP2385216A2 EP2385216A2 (de) 2011-11-09
EP2385216A3 EP2385216A3 (de) 2014-02-19
EP2385216B1 true EP2385216B1 (de) 2018-05-09

Family

ID=44244933

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11157143.6A Active EP2385216B1 (de) 2010-05-06 2011-03-07 Turbinenschaufel mit Gehäuse-Mikrokanälen, die in der Plattform enden

Country Status (2)

Country Link
US (1) US9121290B2 (de)
EP (1) EP2385216B1 (de)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8753083B2 (en) * 2011-01-14 2014-06-17 General Electric Company Curved cooling passages for a turbine component
US9296039B2 (en) 2012-04-24 2016-03-29 United Technologies Corporation Gas turbine engine airfoil impingement cooling
US9243502B2 (en) 2012-04-24 2016-01-26 United Technologies Corporation Airfoil cooling enhancement and method of making the same
US9422817B2 (en) 2012-05-31 2016-08-23 United Technologies Corporation Turbine blade root with microcircuit cooling passages
US20160017724A1 (en) * 2013-04-03 2016-01-21 United Technologies Corporation Variable thickness trailing edge cavity and method of making
EP3034803A1 (de) 2014-12-16 2016-06-22 Rolls-Royce Corporation Hängersystem für eine turbinenmotorkomponente
US10502066B2 (en) 2015-05-08 2019-12-10 United Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10323524B2 (en) * 2015-05-08 2019-06-18 United Technologies Corporation Axial skin core cooling passage for a turbine engine component
US10753210B2 (en) * 2018-05-02 2020-08-25 Raytheon Technologies Corporation Airfoil having improved cooling scheme

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060093480A1 (en) * 2004-11-02 2006-05-04 United Technologies Corporation Airfoil with three-pass serpentine cooling channel and microcircuit
US20070020100A1 (en) * 2005-07-25 2007-01-25 Beeck Alexander R Cooled turbine blade or vane for a gas turbine, and use of a turbine blade or vane of this type
US7527475B1 (en) * 2006-08-11 2009-05-05 Florida Turbine Technologies, Inc. Turbine blade with a near-wall cooling circuit

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1066387B (de) 1955-03-01 1959-10-01
US6354797B1 (en) * 2000-07-27 2002-03-12 General Electric Company Brazeless fillet turbine nozzle
US7364405B2 (en) * 2005-11-23 2008-04-29 United Technologies Corporation Microcircuit cooling for vanes
US7695246B2 (en) * 2006-01-31 2010-04-13 United Technologies Corporation Microcircuits for small engines
US20080008599A1 (en) * 2006-07-10 2008-01-10 United Technologies Corporation Integral main body-tip microcircuits for blades
DE602007008996D1 (de) 2006-07-18 2010-10-21 United Technologies Corp In Schaufelplattform, Schaufelspitze und Schaufelblatt integrierte Mikrokanäle für Turbinenschaufeln
US7686582B2 (en) 2006-07-28 2010-03-30 United Technologies Corporation Radial split serpentine microcircuits
US7927073B2 (en) * 2007-01-04 2011-04-19 Siemens Energy, Inc. Advanced cooling method for combustion turbine airfoil fillets
US7712316B2 (en) * 2007-01-09 2010-05-11 United Technologies Corporation Turbine blade with reverse cooling air film hole direction
US8105033B2 (en) * 2008-06-05 2012-01-31 United Technologies Corporation Particle resistant in-wall cooling passage inlet

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060093480A1 (en) * 2004-11-02 2006-05-04 United Technologies Corporation Airfoil with three-pass serpentine cooling channel and microcircuit
US20070020100A1 (en) * 2005-07-25 2007-01-25 Beeck Alexander R Cooled turbine blade or vane for a gas turbine, and use of a turbine blade or vane of this type
US7527475B1 (en) * 2006-08-11 2009-05-05 Florida Turbine Technologies, Inc. Turbine blade with a near-wall cooling circuit

Also Published As

Publication number Publication date
US20110274559A1 (en) 2011-11-10
US9121290B2 (en) 2015-09-01
EP2385216A3 (de) 2014-02-19
EP2385216A2 (de) 2011-11-09

Similar Documents

Publication Publication Date Title
EP2385216B1 (de) Turbinenschaufel mit Gehäuse-Mikrokanälen, die in der Plattform enden
US7731481B2 (en) Airfoil cooling with staggered refractory metal core microcircuits
EP1070829B1 (de) Strömungsmaschinenschaufel mit innerer Kühlung
US8734108B1 (en) Turbine blade with impingement cooling cavities and platform cooling channels connected in series
US8291963B1 (en) Hybrid core assembly
JP4948797B2 (ja) ガスタービンエンジンロータブレードを冷却するための方法及び装置
EP1813776B1 (de) Mikrokühlkanal für kleine Gasturbinenschaufel
EP2532457B1 (de) Hybridkernanordnung für einen Gussprozess
JP4731238B2 (ja) ガスタービンエンジンロータブレードを冷却するための装置
US7278827B2 (en) Cooling air evacuation slots of turbine blades
US10781716B2 (en) Blade outer air seal cooling scheme
US7303375B2 (en) Refractory metal core cooling technologies for curved leading edge slots
EP1942251B1 (de) Gekühlte Schaufel mit reduzierten Durchfluss durch die Abströmkantenschlitzen und zugehöriges Giessverfahren
EP1936118A2 (de) Gusskernmodifikationen an Turbinenschaufeln für periphere serpentinenartige Mikrokanäle
EP3015189A1 (de) Formartikel zur herstellung von gasturbinenmotorteilen
EP2143512A1 (de) Giesssystem für den Feinguss
US9669458B2 (en) Micro channel and methods of manufacturing a micro channel
EP3015190A1 (de) Formartikel zur herstellung von gasturbinenmotorteilen
EP1621725B1 (de) Turbinenlaufschaufel und Rotor eines Gasturbinentriebwerks mit solchen Schaufeln
US20210121945A1 (en) Cast-in film cooling hole structures

Legal Events

Date Code Title Description
AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/18 20060101AFI20140110BHEP

17P Request for examination filed

Effective date: 20140815

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

17Q First examination report despatched

Effective date: 20150226

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20171122

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 997741

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180515

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602011048177

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180509

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180809

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180809

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180810

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 997741

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180509

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602011048177

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20190212

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190307

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190307

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180910

Ref country code: MT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190307

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180909

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20110307

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180509

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602011048177

Country of ref document: DE

Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, FARMINGTON, CONN., US

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230519

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240220

Year of fee payment: 14

Ref country code: GB

Payment date: 20240220

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240220

Year of fee payment: 14